Manned ducted aircraft cabin structure

Abstract

A manned ducted aircraft cabin structure comprises a fuselage, a plurality of ducted drivers are fixedly connected to the two sides of the fuselage, a cabin is arranged in the fuselage, a replacement assembly is detachably installed in the cabin, and the replacement assembly is connected with the cabin through a quick release assembly; through the detachable cabin structure, seats or goods shelves in the cabin can be conveniently replaced, the functions of the ducted aircraft can be conveniently converted, people carrying or object carrying can be carried out, a manual driving mode or an unmanned automatic driving mode can be adopted during people carrying, the unmanned automatic driving mode is adopted during object carrying, and one aircraft has two purposes.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and more specifically to a cabin structure for a manned ducted aircraft. Background Technology

[0002] Aircraft can be classified into fixed-wing, rotary-wing, and ducted-wing types according to their functions. Ducted-wing aircraft are currently the most advanced type of aircraft. Most ducted-wing aircraft are currently single-tube ducted-wing aircraft, which are only suitable for low-altitude and low-speed flight. Due to limitations in the power of a single engine and rotational inertia, the load-bearing capacity of single-tube ducted-wing aircraft cannot be significantly improved, and their structure is relatively complex. Multi-body ducted-wing aircraft have a relatively strong load-bearing capacity, and manned ducted-wing aircraft mostly adopt a multi-body ducted-wing design.

[0003] Generally, ducted ducted aircraft are only designed for carrying passengers. If cargo needs to be carried, a cargo compartment needs to be installed under the fuselage. However, most passenger aircraft do not have the capability to be modified for safety reasons. In such cases, a separate cargo aircraft is required. Utility Model Content

[0004] One advantage of this utility model is that it provides a cabin structure for a manned ducted jet aircraft. The detachable cabin structure makes it easy to replace the seats or cargo racks inside the cabin, and it is easy to switch the functions of the ducted jet aircraft. It can carry people or cargo. When carrying people, it can be driven manually or in an unmanned autopilot mode. When carrying cargo, it can be driven in an unmanned autopilot mode, making it a dual-purpose aircraft.

[0005] To achieve at least one of the above advantages of this utility model, this utility model provides a manned ducted aircraft cabin structure, including a fuselage, several ducted drive units fixedly connected to both sides of the fuselage, a cabin inside the fuselage, and a replacement component installed inside the cabin in a detachable manner, the replacement component being connected to the cabin by a quick-release component.

[0006] According to one embodiment of the present invention, the quick-release assembly includes two sets of slide rails fixedly installed on the rear wall of the cabin. The slide rails include a back plate and side plates located on both sides of the back plate. A stop bar is provided on the front side of the side plate, and a gap is provided between the two stop bars.

[0007] According to one embodiment of the present invention, both sets of slide rails are vertically arranged and parallel to each other.

[0008] According to one embodiment of the present invention, the replacement component includes a seat, and a slide bar adapted to the slide rail is fixedly provided on the back of the seat. The slide bar includes a vertical plate, and a limiting plate perpendicular to the vertical plate is fixedly provided at the end of the vertical plate. The thickness of the vertical plate is less than the width of the gap between the two baffles, and the width of the limiting plate is equal to the distance between the two side plates.

[0009] According to one embodiment of the present invention, the replacement component further includes a shelf, the front of which is provided with a cargo compartment, and the back of which is fixedly provided with a slide bar adapted to the slide rail. The slide bar includes an upright plate, and the end of the upright plate is fixedly provided with a limiting plate perpendicular to the upright plate. The thickness of the upright plate is less than the width of the gap between the two baffles, and the width of the limiting plate is equal to the distance between the two side plates.

[0010] According to one embodiment of the present invention, the upright plate is further provided with a plurality of grooves, and a roller is rotatably arranged inside the groove, and the roller contacts the stop bar in a rolling manner.

[0011] According to one embodiment of the present invention, a hatch is also provided on the fuselage in a flip-out manner. The hatch is located on the upper part of the cabin and is used to close the cabin.

[0012] According to one embodiment of the present invention, a landing gear is also fixedly installed on the lower part of the fuselage. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the external structure of this utility model;

[0014] Figure 2 This is a schematic diagram of the internal structure of this utility model;

[0015] Figure 3 This is a schematic diagram of the shelf structure of this utility model;

[0016] In the attached diagram: 1. Fuselage, 2. Duct drive, 3. Cabin cover, 4. Slide rail, 5. Rack, 6. Limit plate, 7. Roller, 8. Stand plate. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of this utility model clearer, the following description will be provided in conjunction with the appendix of this utility model. Figure 1 ~Attached Figure 3 The present invention will be described in more detail below.

[0018] The following description is intended to disclose the present invention so that those skilled in the art can implement it. The preferred embodiments described below are merely examples, and other obvious variations will occur to those skilled in the art. The basic principles of the present invention defined in the following description can be applied to other embodiments, modifications, improvements, equivalents, and other technical solutions that do not depart from the spirit and scope of the present invention.

[0019] Those skilled in the art should understand that, in the disclosure of this specification, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, the above terms should not be construed as limitations on this utility model.

[0020] It is understood that the term "a" should be understood as "at least one" or "one or more", that is, in one embodiment, the number of an element can be one, while in another embodiment, the number of the element can be multiple, and the term "a" should not be understood as a limitation on the number.

[0021] This utility model provides a manned ducted jet aircraft cabin structure, including a fuselage 1. Several ducted drive units 2 are fixedly connected to both sides of the fuselage 1. A cabin is located inside the fuselage 1, and a replacement assembly is detachably installed inside the cabin. The replacement assembly is connected to the cabin via a quick-release assembly. The quick-release assembly includes two sets of slide rails 4 fixedly installed on the rear wall of the cabin. Each slide rail 4 includes a back plate and side plates located on both sides of the back plate. A stop bar is provided on the front side of each side plate, and a gap is provided between the two stop bars. Both sets of slide rails 4 are vertically arranged and parallel to each other. The replacement assembly includes a seat. A slide bar adapted to the slide rails 4 is fixedly installed on the back of the seat. The slide bar includes a vertical plate 8, and a limiting plate 6 perpendicular to the vertical plate 8 is fixedly installed at the end of the vertical plate 8. The thickness of the vertical plate 8 is... The width of the limit plate 6 is equal to the distance between the two side plates, which is less than the width of the gap between the two stop bars. The replacement component also includes a shelf 5, which has a cargo compartment at the front and a slide bar adapted to the slide rail 4 fixedly installed on the back of the shelf 5. The slide bar includes a vertical plate 8, and a limit plate 6 perpendicular to the vertical plate 8 is fixedly installed at the end of the vertical plate 8. The thickness of the vertical plate 8 is less than the width of the gap between the two stop bars, and the width of the limit plate 6 is equal to the distance between the two side plates. The vertical plate 8 is also provided with several grooves, and rollers 7 are rotatably installed inside the grooves. The rollers 7 contact the stop bars in a rolling manner. The fuselage 1 is also provided with a hatch 3 that can be flipped up. The hatch 3 is located on the upper part of the cabin and is used to close the cabin. The lower part of the fuselage 1 is also fixedly provided with landing gear.

[0022] The first embodiment of this utility model is as follows:

[0023] A manned ducted jet aircraft cabin structure includes a fuselage 1, with four ducted drive 2 mounting positions fixedly connected to both sides of the fuselage 1. After the ducted drive 2 is installed, a two-position distributed thrust array structure is formed. The four ducted drive 2 form a lift drive system in a two-dimensional space, i.e., a planar layout, and each ducted drive 2 is part of the lift drive system. The lift drive system includes a front left lift module, a front right lift module, a rear left lift module, and a rear right lift module, located on the front left, front right, rear left, and rear right sides of the fuselage 1, respectively. Each module is equipped with at least one permanent magnet synchronous motor and an FOC controller. The FOC controller is used to control the flux linkage and torque of the permanent magnet synchronous motor. The ducted drive 2 can rotate to change the direction of the driving force, thereby enabling the ducted aircraft to take off, land, and fly. When the ducted aircraft takes off vertically, all modules of the lift drive system are in a horizontal state, and all four modules rotate on the same horizontal plane, generating lift in a vertically downward direction. When the ducted aircraft flies horizontally, all modules of the lift drive system are in an inclined state, and all four modules rotate at similar inclination angles, generating lift in an inclined rearward direction. Through force analysis, the UAV can maintain forward flight while maintaining the same altitude. When the ducted jet hovers, all modules of the lift drive system are in a horizontal state, and all four modules rotate on the same horizontal plane. The lift generated is vertically downward. At this time, the drone will be affected by crosswinds, which will cause it to receive lateral forces, resulting in a tendency for the drone to move horizontally.

[0024] The fuselage 1 houses a battery that provides power to the motors of the ducted drive 2 via a power management system. The fuselage 1 also houses a control system, including a flight controller comprising multiple independent control computers using non-volatile computer-readable storage media. This storage medium contains one or more sets of computer instructions, readable by the control computers, for controlling the operation of the ducted aircraft. Preferably, the flight controller is a processor-based control system capable of executing program code in the form of machine-executable instructions. It connects to other control terminals via a communication network for remote control, including both wired and wireless connections.

[0025] Meanwhile, the control method can adopt manual driving or unmanned driving mode. A driving device is installed at the front of the cabin. There are mature system architectures available for both manual driving and unmanned driving modes, which will not be elaborated here.

[0026] The fuselage 1 has a cabin inside, where seats or cargo racks 5 can be installed. When seats are installed, people can be carried, and when cargo racks 5 are installed, goods can be carried. The fuselage 1 also has a flip-up hatch 3, which is located on the upper part of the cabin and is used to close the cabin. The lower part of the fuselage 1 is also fixedly equipped with landing gear.

[0027] Replacement components are installed inside the cabin in a detachable manner, and the replacement components are connected to the cabin using quick-release components.

[0028] The quick-release assembly includes two sets of slide rails 4 fixedly installed on the rear wall of the cabin. Both sets of slide rails 4 are vertically arranged and parallel to each other. Each slide rail 4 includes a back plate and side plates located on both sides of the back plate. A baffle is provided on the front side of the side plate, and a gap is provided between the two baffles. The back plate, side plates and baffles form a space with openings at the top and bottom, and communicate with the gap to form a structure for installing and replacing the assembly.

[0029] The replacement components include a seat or shelf 5. The front of the seat is the seating position for the driver or passenger. The front of the shelf 5 is provided with a cargo compartment. The back of the seat or shelf 5 is fixedly provided with a slide bar adapted to the slide rail 4. The slide bar includes a vertical plate 8. The end of the vertical plate 8 is fixedly provided with a limiting plate 6 perpendicular to the vertical plate 8. The thickness of the vertical plate 8 is less than the width of the gap between the two baffles. The width of the limiting plate 6 is equal to the distance between the two side plates. In use, the limiting plate 6 can be inserted into the space enclosed by the back plate, side plates and baffles, which can both install the seat or shelf 5 inside the cabin and also serve as a limiting function.

[0030] To solve the problem of obstruction during the disassembly or installation of the seat or shelf 5, several grooves are provided on the upright plate 8. Rollers 7 are rotatably installed inside the grooves. The rollers 7 make rolling contact with the stop bar. When installing or disassembling the seat or shelf 5, the sliding friction between the limit plate 6 and the stop bar is changed to rolling friction, making the installation or disassembly smoother.

[0031] When in use, the machine can carry people by installing a seat, and can be driven manually or automatically. After removing the seat, the machine can be replaced with a shelf 5, and goods can be placed on the shelf 5. In the automatic mode, goods can be transferred, thus achieving a dual-purpose function.

[0032] It should be noted that the terms "first, second, and third" used in this utility model are for descriptive purposes only and do not indicate any order. They should not be construed as indicating or implying relative importance, and can be interpreted as names.

[0033] Those skilled in the art should understand that the embodiments of the present invention described above and shown in the accompanying drawings are merely examples and do not limit the present invention. The advantages of the present invention have been fully and effectively realized. The functional and structural principles of the present invention have been shown and explained in the embodiments. Without departing from the principles, the implementation of the present invention may have any modifications or variations.

Claims

1. A manned ducted aircraft cabin structure, comprising a fuselage, a plurality of ducted drives are fixedly connected on both sides of the fuselage, characterized in that: The fuselage is equipped with a cabin, and a replacement component is installed inside the cabin in a detachable manner. The replacement component is connected to the cabin by a quick-release assembly.

2. The manned ducted aircraft cabin structure of claim 1, wherein: The quick-release assembly includes two sets of slide rails fixedly installed on the rear wall of the cabin. The slide rails include a back plate and side plates located on both sides of the back plate. A stop bar is provided on the front side of the side plate, and a gap is provided between the two stop bars.

3. The manned ducted aircraft cabin structure of claim 2, wherein: Both sets of slide rails are vertically arranged and parallel to each other.

4. The manned ducted aircraft cabin structure of claim 2, wherein: The replacement component includes a seat, on the back of which a slide bar adapted to a slide rail is fixedly provided. The slide bar includes a vertical plate, and a limiting plate perpendicular to the vertical plate is fixedly provided at the end of the vertical plate. The thickness of the vertical plate is less than the width of the gap between the two side plates, and the width of the limiting plate is equal to the distance between the two side plates.

5. The manned ducted aircraft cabin structure of claim 2, wherein: The replacement component also includes a shelf, the front of which is provided with a cargo compartment, and the back of which is fixedly provided with a slide bar adapted to the slide rail. The slide bar includes an upright plate, and the end of the upright plate is fixedly provided with a limiting plate perpendicular to the upright plate. The thickness of the upright plate is less than the width of the gap between the two side plates, and the width of the limiting plate is equal to the distance between the two side plates.

6. The manned ducted aircraft cabin structure of any one of claims 4 or 5, wherein: The upright plate is also provided with several grooves, and rollers are rotatably arranged inside the grooves. The rollers contact the stop bar in a rolling manner.

7. The manned ducted aircraft cabin structure of claim 1, wherein: The fuselage is also equipped with a flip-up hatch, which is located on the upper part of the cabin and is used to close the cabin.

8. The manned ducted aircraft cabin structure of claim 1, wherein: The lower part of the fuselage is also fixedly equipped with landing gear.

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